A fixed-wing UAV wing testing device

Abstract

This invention relates to the field of fixed-wing UAV wing testing technology, specifically to a fixed-wing UAV wing testing device, comprising: a testing platform and a testing frame fixed above the testing platform; multiple testing seats, all movably arranged along the testing frame via electric slide rails and electric sliders; an actuator is provided within each testing seat, the actuator comprising: an amplification component having a contact seat for contacting the upper surface of the wing and for amplifying and outputting the displacement of the contact seat caused by wing deformation under load; and a transient impact component including a sliding block, a return spring, and a conformal impact block mounted at the bottom of the sliding block. This invention realistically simulates the mechanical response of a wing encountering downward inertial loads or aerodynamic disturbances under high lift conditions, upgrading the test results from simple strength compliance to verification of dangerous load combinations, thus enhancing the engineering reference value for fixed-wing UAV wing testing.

Description

Technical Field

[0001] This invention relates to the field of fixed-wing unmanned aerial vehicle (UAV) wing testing technology, and more specifically to a fixed-wing UAV wing testing device. Background Technology

[0002] Fixed-wing unmanned aerial vehicles (UAVs) have been widely deployed in reconnaissance and surveillance, border patrol, electronic warfare, target drone training, and cargo delivery due to their advantages such as long flight time, long range, and large payload. As the core component for generating lift in fixed-wing UAVs, the wing bears complex aerodynamic and inertial loads during flight, and its structural strength directly determines flight safety and mission success rate. Therefore, after the UAV is assembled and before it is delivered for use, the wing must undergo thorough and rigorous ground load testing and strength inspection.

[0003] Existing testing methods for UAV wings mainly include static load testing and drop hammer (pendulum) dynamic impact testing. Static testing typically uses electric actuators, hydraulic actuators, or counterweights to apply simulated lift from below the wing, detecting the deformation and failure threshold of the wing under static load. Dynamic impact testing, on the other hand, applies a transient impact force from above the wing through free fall or spring release to assess the wing's impact resistance. However, both types of testing share a common flaw in their testing logic: static load and impact are completely separated, making it impossible to superimpose a transient downward impact load while the wing is in a state of extreme bending deformation during the same test process.

[0004] In the actual flight profile of fixed-wing UAVs, the wings often face the most dangerous conditions of high static load combined with downward transient load. For example, if a fixed-wing UAV enters a micro-downburst region during a mission, it will encounter a strong downward airflow component in a very short time. At this time, the wing is in a high lift state during cruise or maneuvering. The downdraft induces transient downward aerodynamic disturbances on the upper surface of the wing. The wing is under extreme bending stress, and the transient downward load is superimposed, inducing structural instability or wing surface tearing. This load combination will cause the wing to experience stress redistribution and transient superposition simultaneously in the maximum tensile stress area (lower surface skin and lower edge spar) and the maximum compressive stress area (upper surface skin and upper edge spar), which is a dangerous stress state that can induce spar crack propagation, skin wrinkling, or even the failure of the entire structure. However, existing testing equipment cannot reproduce this critical condition at all.

[0005] To address this, we designed a wing testing device for fixed-wing UAVs. Summary of the Invention

[0006] The purpose of this invention is to solve the problems existing in the prior art by proposing a fixed-wing unmanned aerial vehicle (UAV) wing testing device.

[0007] To achieve the above objectives, the present invention adopts the following technical solution: A fixed-wing unmanned aerial vehicle (UAV) wing testing device, comprising: The testing platform, and the testing frame fixed above the testing platform, provide stable installation support for each moving part; Multiple detection seats are movably arranged along the detection frame via electric slide rails and electric sliders for positioning at a preset position above the wing; The detection base is equipped with an actuator, which includes: The amplification component has a contact seat for contacting the upper surface of the wing and for amplifying the displacement of the contact seat caused by the load deformation of the wing. The transient impact component includes a sliding block, a return spring, and a contoured impact block installed at the bottom of the sliding block. The sliding block is slidably arranged in the vertical direction. The return spring is driven and connected to the sliding block. It stores energy as the sliding block retracts upward and releases the sliding block to move downward when unlocked, so as to simulate the static limit bending of the wing in conjunction with the downward transient superimposed load. A triggering component is connected between the output end of the amplification component and the sliding block. It is used to transmit the amplified displacement to the sliding block and trigger the locking release of the sliding block when the sliding block reaches the high energy storage position.

[0008] Preferably, the amplification component includes: A slot is formed in the bottom wall of the testing seat; A rotating shaft is connected to the inner wall of the empty groove in a way that limits the rotation angle, and is elastically connected to the inner wall of the empty groove through a torsion spring, so that the rotating shaft maintains its initial posture when it is not subjected to external force. The trigger rod has the contact seat installed at one end, and the trigger rod is fixedly connected to the rotating shaft, forming a lever structure with the rotating shaft as the fulcrum, which amplifies the small displacement of the contact seat into the amplified displacement of the free end of the trigger rod.

[0009] Preferably, there are two rotating shafts and two trigger rods, with different widths. One trigger rod has an opening on its top wall, and the other trigger rod passes through the opening to avoid motion interference.

[0010] Preferably, the transient impact component further includes: Two vertical grooves are formed on the top inner wall of the empty groove, and the sliding block is slidably disposed in the groove; One end of the reset spring is fixedly connected to the top inner wall of the slide groove, and the other end is fixedly connected to the sliding block.

[0011] Preferably, a limiting groove is formed on the side wall of the sliding block, and a wedge plate is elastically connected in the limiting groove by a limiting spring.

[0012] Preferably, the triggering component includes: The sliding rack slides vertically to the inner wall of the slot; The drive rod is fixed to the side wall of the sliding rack; A sliding hole is provided at the end of the trigger rod away from the contact seat. The drive rod is inserted into the sliding hole and can slide and abut against each other in the hole, converting the swing of the trigger rod into the vertical movement of the sliding rack. A precision gear is rotatably connected to the inner wall of the slot and meshes with the sliding rack. The toothed plate is slidably connected to the inner wall of the slot and meshes with the precision gear. The toothed plate and the sliding rack are respectively located on both sides of the precision gear and move in opposite directions. A push rod is fixed to the toothed plate, and its upper end abuts against the wedge plate; The wedge plate has a protrusion fixed to its side wall, and the slot has a wedge strip fixed to its inner wall. The wedge strip is located above the movement path of the wedge plate and has a guide slope. When the push rod pushes the wedge plate and the sliding block to move upward until the protrusion contacts the wedge strip, the wedge plate is squeezed into the limiting groove by the slope, releasing the locking of the sliding block.

[0013] Preferably, it further includes: a loading unit disposed on the testing platform for applying an upward simulated load to the lower surface of the wing, comprising: Multiple detachable power mounts that can be installed on the testing table; Each power unit has an electric push rod embedded in its top wall. The movable end of the electric push rod is fixed to a contour block. The top wall of the contour block is embedded with a pressure sensor. The pressure sensor is electrically connected to the controller of the electric push rod to realize closed-loop control of the loading force.

[0014] Preferably, the testing platform is also equipped with a clamping device for stabilizing and clamping the drone's wings.

[0015] Compared with existing technologies, the advantages of this invention are: Compared to existing equipment that separates static load and impact testing (where the impact timing is independent of wing deformation), this invention utilizes the wing's own ultimate bending deformation as a trigger source. A mechanical transmission chain automatically unlocks and releases the reset spring, ensuring that the downward transient impact is precisely applied at the moment of highest stress concentration on the wing. This loading mode, combining static ultimate bending with downward transient impact, realistically simulates the mechanical response of a wing encountering downward inertial loads or aerodynamic disturbances under high lift conditions. This upgrades the test results from simply verifying strength compliance to validating dangerous load combinations, enhancing the engineering reference value and flight safety margin for fixed-wing UAV wing testing. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the appearance of a fixed-wing UAV wing testing device proposed in this invention; Figure 2 for Figure 1 Enlarged schematic diagram of section A of the structure; Figure 3 This is a schematic diagram of the vertical cross-section of the testing seat in a fixed-wing UAV wing testing device proposed in this invention; Figure 4 for Figure 2 Enlarged schematic diagram of section B of the structure; Figure 5 This is a schematic diagram of the internal structure of the testing seat in a fixed-wing UAV wing testing device proposed in this invention; Figure 6 for Figure 5 Enlarged schematic diagram of the C-section structure; Figure 7 for Figure 5 Enlarged schematic diagram of the structure of section D in the middle; Figure 8 This is a schematic diagram of the structure of a drone proposed in this invention.

[0017] In the diagram: 1. Testing platform; 2. Testing frame; 4. Power unit; 5. Loading unit; 51. Electric actuator; 52. Profile block; 53. Pressure sensor; 6. Enlarging component; 61. Torsion spring; 62. Hole; 63. Rotating shaft; 64. Trigger rod; 65. Contact seat; 66. Opening; 7. Trigger assembly; 71. Sliding rack; 72. Drive rod; 73. Sliding hole; 74. Precision gear; 75. Gear plate; 76. Push rod; 77. Wedge plate; 78. Protrusion; 79. Wedge strip; 8. Transient impact component; 81. Slide groove; 82. Return spring; 83. Sliding block; 84. Limiting groove; 85. Limiting spring; 86. Contouring impact block; 9. Electric slide rail; 10. Electric slider; 11. Unmanned Aerial Vehicle (UAV) body; 111. Wings; 112. Propellers; 12. Detection seat; 13. Clamping device. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] Reference Figures 1-8 A fixed-wing unmanned aerial vehicle (UAV) wing testing device, comprising: The testing platform 1 serves as the overall load-bearing and positioning unit, and the testing frame 2 is vertically fixed above the testing platform 1. The testing frame 2 has a gate-shaped structure, providing stable installation support for each moving component.

[0020] An electric slide rail 9 is fixedly connected to the inner wall of the detection frame 2. Multiple independently lockable electric sliders 10 are slidably mounted on the electric slide rail 9. Each electric slider 10 is fixedly mounted with a detection seat 12 (e.g., ...). Figure 1 (As shown); the detection seat 12 can move precisely along the slide rail with the electric slider 10 to reach different detection points on the drone wing, and by setting multiple detection seats 12, multiple detection points on the drone wing can be tested simultaneously.

[0021] Multiple power seats 4 are detachably mounted on the testing table 1. The power seats 4 are correspondingly arranged with the testing table 12, and each power seat 4 has a loading unit 5 on its top wall (in conjunction with...). Figure 1 and Figure 2 As shown, the loading unit 5 includes an electric push rod 51 embedded in the top wall of the power seat 4. A contour block 52 is fixedly connected to the movable end of the electric push rod 51. A pressure sensor 53 is embedded and fixed in the top wall of the contour block 52. The pressure sensor 53 is electrically connected to the controller of the electric push rod 51. The shape of the contour block 52 is adapted to the contour of the lower surface of the wing. Through the real-time feedback of the pressure sensor 53, the electric push rod 51 can apply a precise and controllable simulated lift or concentrated load to the wing.

[0022] The testing mount 12 is equipped with an actuator for simulating load tests on the wings of the UAV. This actuator can sense the minute deformation of the wings after being loaded and conduct further dynamic mechanical tests on the wings accordingly. The implementing agencies include: Amplifying component 6 includes: The slot 62 opened on the bottom wall of the detection seat 12 (e.g.) Figure 5 (as shown) Rotation axis 63 (e.g.) Figure 4 As shown), they are connected to the inner wall of the slot 62 in a way that restricts the rotation angle, that is, the rotating shaft 63 can only rotate within a set small angle range, and each rotating shaft 63 is elastically connected to the inner wall of the slot 62 through a torsion spring 61, that is, one end of the torsion spring 61 is fixed to the rotating shaft 63, and the other end of the torsion spring 61 is fixed to the inner wall of the slot 62, so that the rotating shaft 63 maintains its initial posture when it is not subjected to external force; The contact seat 65 is used to make contact with the upper surface of the drone wing. When the wing bends or twists under load, the contact seat 65 can move slightly. The trigger rod 64 is fixed to the side wall of each rotating shaft 63. A contact seat 65 is installed at one end of the trigger rod 64. The trigger rod 64, the rotating shaft 63, and the contact seat 65 together form a lever structure to amplify the small displacement sensed at the contact seat 65 into a more significant displacement output at the free end of the trigger rod 64.

[0023] Furthermore, the two trigger rods 64 have different widths, and one of the trigger rods 64 has an opening 66 on its top wall (e.g., Figure 4 As shown), another trigger rod 64 passes through the opening 66 to avoid interference between the two trigger rods 64.

[0024] It also includes: transient impact component 8; which includes: Two vertical grooves 81 are both formed on the inner wall of the top of the empty groove 62 (in conjunction with...) Figure 5 and Figure 7 (as shown) The sliding block 83 is elastically connected to the inner wall of the slide groove 81 via a return spring 82, and the sliding block 83 can slide vertically within the slide groove 81. The bottom wall of the sliding block 83 is detachably equipped with a contoured impact block 86. The lower surface contour of the contoured impact block 86 matches the impact area on the upper surface of the wing. The lower surface of the contoured impact block 86 is a flexible contact surface adapted to the contour of the impact area on the upper surface of the wing. Its contact area covers a local area of ​​the upper surface of the wing. It is used to apply a transient downward force to the wing in a surface contact manner when released, rather than a rigid point contact impact.

[0025] The purpose of the contour impact block 86 is to construct a transient impact mechanism, that is, to superimpose a mechanical energy storage and release unit on the static load path formed by the electric push rod 51. Its core principle is: during the test, the trigger component 7 drives the wedge plate 77 to retract and unlock, thereby causing the return spring 82 to be released instantaneously, pushing the contour impact block 86 to rush downwards rapidly; if the impact characteristics need to be adjusted, an adjustable stroke buffer damper (such as hydraulic damping or friction damping structure) can be added to the sliding path of the sliding block 83, thereby generating a short-duration, high-amplitude downward force pulse. This pulse is directly superimposed on the static simulated load applied by the electric push rod 51, providing a wing structure severity test device that superimposes transient downward impact on the static ultimate load, to simulate the transient structural response of the wing when it encounters external impact disturbance under ultimate lift state, thereby evaluating the wing's resistance to damage.

[0026] The side wall of the sliding block 83 is provided with a limit groove 84 (combined with) Figure 5 and Figure 6 As shown), the inner wall of the limiting groove 84 is elastically connected to a horizontally retractable wedge plate 77 via a limiting spring 85; the wedge plate 77 extends out of the limiting groove 84 in its normal state.

[0027] The transient impact component 8 also includes a triggering component 7, which comprises: Two sliding racks 71 are slidably connected to the inner sidewall of the slot 62 in a vertical direction; The sliding hole 73 is a rectangular hole, which is opened on the side wall of each trigger rod 64 away from the contact seat 65; A drive rod 72 is fixed to the side wall of the sliding rack 71. The drive rod 72 is inserted into the sliding hole 73 on the corresponding trigger rod 64 and can slide against each other in the rectangular hole, thereby converting the swing of the trigger rod 64 into the vertical movement of the sliding rack 71.

[0028] Two precision gears 74 are rotatably connected to the inner sidewall of the slot 62; The sliding rack 71 is meshed with the precision gear 74. The inner wall of the slot 62 is also slidably connected to the toothed plate 75 via the guide rail. The toothed plate 75 is also meshed with the precision gear 74. The toothed plate 75 and the sliding rack 71 are located on opposite sides of the precision gear 74, so that their movement directions are opposite.

[0029] A push rod 76 is fixedly connected to the side wall of the toothed plate 75; a protrusion 78 is fixedly connected to the side wall of the wedge plate 77, and the push rod 76 abuts against the wedge plate 77; after moving a certain distance, the protrusion 78 slides against the wedge strip 79, and the movement path of the push rod 76 is offset from the installation position of the wedge strip 79, so they do not interfere with each other.

[0030] A wedge-shaped strip 79 is installed on the inner wall of the slot 62. The wedge-shaped strip 79 is located on the movement path of the wedge plate 77 and has a guide slope. When the push rod 76 pushes the wedge plate 77 to move, when the protrusion 78 contacts the slope of the wedge-shaped strip 79, the wedge plate 77 is forced to overcome the elastic force of the limiting spring 85 and retract into the limiting slot 84, releasing the lock on the sliding block 83. At this time, the reset spring 82 instantly releases the accumulated elastic potential energy, driving the sliding block 83 and the contour impact block 86 to quickly impact downward, completing the instantaneous dynamic load application on the UAV wing.

[0031] The wedge strip 79 can be adjusted by adjusting the bolt or by adjusting its position in the vertical direction, thereby changing the energy storage displacement of the sliding block 83 when the protrusion 78 contacts the wedge strip 79. When multiple detection seats 12 are tested simultaneously, the triggering components 7 of each detection seat 12 work independently, triggering transient impacts according to the actual deformation of the wing at their respective contact seats 65. To achieve synchronized impacts, the height of the wedge strip 79 in each detection seat 12 can be adjusted, thereby adjusting the triggering threshold at each point, so that the wing can be unlocked simultaneously when the entire wing reaches a preset bending state.

[0032] The mechanical thrust of push rod 76 drives the sliding block 83 to move smoothly upward. Push rod 76 ensures that the triggering timing is mechanically synchronized with the actual deformation of the wing. That is, during the process of the wing bending deformation driving push rod 76 to move upward, push rod 76 provides the sole mechanical driving force, pushing wedge plate 77 and sliding block 83 upward and compressing return spring 82 to store energy. In this process, return spring 82 only acts as a passive energy storage element, and its reaction force is borne by the mechanical locking state of wedge plate 77 and is not transmitted in the reverse direction to contact seat 65 through the transmission chain. The upward displacement of sliding block 83 is entirely determined by the displacement of push rod 76.

[0033] When the wing bends to the preset limit, the return spring 82 retracts to the energy storage high position, and the sliding block 83 retracts to the preset limit position. At this time, the wedge plate 77 retracts into the limiting groove 84. As the potential energy stored in the return spring 82 is released instantaneously, it drives the contour impact block 86 to impact the upper surface of the wing downward, completing the simulation of the ultimate bending superimposed transient impact condition.

[0034] To avoid substantial interference with the static loading of the wing during the energy storage process of the return spring 82, the stiffness of the return spring 82 and the overall leverage ratio of the transmission system should be appropriately selected so that the additional reaction force transmitted to the contact seat 65 does not exceed a preset threshold. A secondary pressure sensor (not shown) can be installed at the contact seat 65 to monitor this additional reaction force in real time, and the spring stiffness or leverage ratio can be adjusted according to the magnitude of the reaction force.

[0035] An external clamping device 13, such as an electric clamp, is installed on the testing table 1 to stably clamp the drone wing and simulate the installation of the drone wing.

[0036] The drone detected in this embodiment includes the drone body 11 and the wings 111 disposed on the drone body 11 (e.g., ...). Figure 8 As shown), a propeller 112 is installed at the front end of the drone body 11, and the wing 111 is tested using the fixed-wing drone wing testing device involved in this invention.

[0037] The detection method of the present invention will be explained in detail below with reference to the accompanying drawings: 1. When using, place the wing of the drone to be tested horizontally on the test platform 1 and hold it stably with the clamping device 13. Adjust and fix multiple power seats 4 according to the wing support position.

[0038] 2. The electric push rod 51 pushes the contour block 52 upward, so that its upper surface is in contact with and presses against the lower surface of the wing. The pressure sensor 53 detects the contact force in real time and feeds it back to the controller to realize closed-loop control of the loading force.

[0039] 3. Subsequently, the electric slider 10 drives the detection seat 12 to a preset position above the wing, so that the contact seat 65 of the magnifying component 6 gently adheres to the upper surface of the wing.

[0040] 4. After the test begins, the electric push rod 51 applies a gradually increasing simulated static load to the wing, causing the wing to bend or twist. The contact seat 65 senses the minute displacement. This displacement is transmitted to the trigger rod 64 through the rotating shaft 63, and after being amplified by the lever, it forms a significant amount of motion at the free end of the trigger rod 64. The sliding hole 73 at the end of the trigger rod 64 drives the drive rod 72, which in turn drives the sliding rack 71 to produce vertical motion. After the precision gear 74 reverses direction, the gear plate 75 moves in the opposite direction, and the push rod 76 on the gear plate 75 pushes the wedge plate 77 and the sliding block 83 upward together, compressing the return spring 82 to store energy.

[0041] 5. When the protrusion 78 moves to contact the inclined surface of the wedge strip 79, the protrusion 78 drives the wedge plate 77 to be forcibly squeezed into the limiting groove 84 by the inclined surface. The locking state of the sliding block 83 is released, the energy stored in the return spring 82 is released instantaneously, and the contour impact block 86 rapidly impacts the upper surface of the wing, thereby generating a short-duration high-amplitude force pulse superimposed on the static load. After the impact is completed, the load is removed, and each component is reset under the action of elastic elements such as the torsion spring 61 and the limiting spring 85, ready for the next round of testing.

[0042] This invention utilizes the loading unit 5 to apply a continuous static lift force to the wing, forcing it to reach a preset limit bending deformation state. Under this preload state, the wing's own deformation displacement is amplified by the amplification component 6, driving the transient impact component 8 to store energy and release it instantaneously. By controlling the timing of pre-bending to the limit and then applying a reverse impact, the downward transient impact load applied to the UAV when the wing is in a limit bending state can be realistically reproduced, thereby improving the comprehensiveness of wing structure testing.

[0043] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A wing testing device for a fixed-wing unmanned aerial vehicle (UAV), comprising: The testing platform (1) and the testing frame (2) fixed above the testing platform (1) provide stable installation support for each moving part; Multiple detection seats (12) are movably arranged along the detection frame (2) via electric slide rails (9) and electric sliders (10) for positioning to a preset position above the wing; The feature is that an actuator is provided inside the detection seat (12), and the actuator includes: The amplification component (6) has a contact seat (65) for contacting the upper surface of the wing and for amplifying and outputting the displacement of the contact seat (65) caused by the deformation of the wing under load; The transient impact component (8) includes a sliding block (83), a return spring (82), and a contoured impact block (86) installed at the bottom of the sliding block (83). The sliding block (83) is slidably arranged in the vertical direction. The return spring (82) is driven to connect with the sliding block (83). It stores energy as the sliding block (83) contracts upward. When unlocked, it releases the sliding block (83) to move downward, so as to simulate the static limit bending of the wing combined with the downward transient superimposed load. The trigger component (7) is connected between the output end of the amplification component (6) and the sliding block (83) to transmit the amplified displacement to the sliding block (83) and trigger the locking release of the sliding block (83) when the sliding block (83) reaches the high energy storage position.

2. The fixed-wing UAV wing testing device according to claim 1, characterized in that, The amplification component (6) includes: A slot (62) is formed in the bottom wall of the detection seat (12); The rotating shaft (63) is connected to the inner wall of the empty groove (62) in a way that limits the rotation angle, and is elastically connected to the inner wall of the empty groove (62) through a torsion spring (61), so that the rotating shaft (63) maintains its initial posture when it is not subjected to external force; The trigger rod (64) has the contact seat (65) installed at one end, and the trigger rod (64) is fixedly connected to the rotating shaft (63) to form a lever structure with the rotating shaft (63) as the fulcrum, which amplifies the small displacement of the contact seat (65) into the amplified displacement of the free end of the trigger rod (64).

3. The fixed-wing UAV wing testing device according to claim 2, characterized in that, There are two rotating shafts (63) and two trigger rods (64). The two trigger rods (64) have different widths. One of the trigger rods (64) has an opening (66) on its top wall, and the other trigger rod (64) passes through the opening (66) to avoid motion interference.

4. The fixed-wing UAV wing testing device according to claim 2, characterized in that, The transient impact component (8) also includes: Two vertical grooves (81) are formed on the top inner wall of the empty groove (62), and the sliding block (83) is slidably disposed in the groove (81); One end of the return spring (82) is fixedly connected to the top inner wall of the slide groove (81), and the other end is fixedly connected to the sliding block (83).

5. A fixed-wing UAV wing testing device according to claim 4, characterized in that, The sliding block (83) has a limiting groove (84) on its side wall, and a wedge plate (77) is elastically connected in the limiting groove (84) by a limiting spring (85).

6. The fixed-wing UAV wing testing device according to claim 5, characterized in that, The triggering component (7) includes: The sliding rack (71) is slidably connected to the inner wall of the slot (62) in the vertical direction; The drive rod (72) is fixed to the side wall of the sliding rack (71); A sliding hole (73) is provided at the end of the trigger rod (64) away from the contact seat (65). The drive rod (72) is inserted into the sliding hole (73) and can slide and abut against each other in the hole, converting the swing of the trigger rod (64) into the vertical movement of the sliding rack (71). A precision gear (74) is rotatably connected to the inner wall of the slot (62) and meshes with the sliding rack (71); The toothed plate (75) is slidably connected to the inner wall of the slot (62) and meshes with the precision gear (74). The toothed plate (75) and the sliding rack (71) are respectively located on both sides of the precision gear (74) and move in opposite directions. The push rod (76) is fixed on the toothed plate (75), and its upper end is in contact with the wedge plate (77); The wedge plate (77) has a protrusion (78) fixed to its side wall, and a wedge strip (79) is fixed to the inner wall of the slot (62). The wedge strip (79) is located above the movement path of the wedge plate (77) and has a guide slope. When the push rod (76) pushes the wedge plate (77) and the sliding block (83) to move up until the protrusion (78) contacts the wedge strip (79), the wedge plate (77) is squeezed into the limiting groove (84) by the slope, releasing the locking of the sliding block (83).

7. The fixed-wing UAV wing testing device according to claim 1, characterized in that, Also includes: A loading unit (5), mounted on the testing platform (1) for applying an upward simulated load to the lower surface of the wing, comprises: Multiple detachable power seats (4) are mounted on the testing table (1); Each power seat (4) has an electric push rod (51) embedded in its top wall. The movable end of the electric push rod (51) is fixed to a contour block (52). The top wall of the contour block (52) is embedded with a pressure sensor (53). The pressure sensor (53) is electrically connected to the controller of the electric push rod (51) to realize closed-loop control of the loading force.

8. The fixed-wing UAV wing testing device according to claim 1, characterized in that, The testing platform (1) is also equipped with a clamping device (13) for stabilizing the drone's wings.

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